JAMP  Vol.2 No.6 , May 2014
Aerodynamic Design of the Bleed Slot in a Hypersonic Quiet Nozzle

The bleed slot is necessary for the requirement of the hypersonic quiet flow all over the world. The aim of the bleed slot is to decrease the influence of the disturbances from the contraction of the quiet nozzle to the boundary layer downstream of the throat, so that the boundary layer of the nozzle could be maintained as laminar flow. The main parameters of the bleed slot include the distance from lip to throat (DLT) and the width of slot (WS). Various values of those parameters will affect the performance of the slot by changing the suction intensity of the bleed slot. Two kinds of the bleed slots in the world are compared in this paper and the aerodynamic design of the bleed slots is optimized based on the Purdue-type slot. The influences of the various values of those parameters to the flow field around the throat are analyzed and the optimizing results of DLT and WS are consistent with those relative data designed for the slot of the Boeing/AFOSR Ma 6 Quiet Tunnel.

Cite this paper: Li, R. , Shen, J. and Ji, F. (2014) Aerodynamic Design of the Bleed Slot in a Hypersonic Quiet Nozzle. Journal of Applied Mathematics and Physics, 2, 437-442. doi: 10.4236/jamp.2014.26053.

[1]   Klebanoff, P.S., Spangenberg, W. and Schubauer, G.B. (1961) Investigation of Boundary Layer Transition. Progress Report of National Bureau of Standards, Available from NASA STI as 62N10625.

[2]   Klebanoff, P.S. and Spangen-berg, W. (1965) Investigation of Boundary Layer Transition. Progress Report of National Bureau of Standards, Available from NASA STI as 65N89192, NASA-CR-67495.

[3]   Kendall Jr., J.M. (1967) Supersonic Boundary Layer Stability Experiments. In: McCauley, W.D. Ed., Boundary Layer Transition Study Group Meeting, Vol. II, Session on Boundary Layer Stability, Aerospace Corp., San Bernardino; also Air Force Rept. BSD-TR-67-213, Vol. 2.

[4]   Kendall Jr., J.M. (1974) Wind Tunnel Experiments Relating to Supersonic and Hypersonic Boundary-Layer Transition. AIAA Paper: 1974-0133.

[5]   Beckwith, I.E. (1975) Development of a High Reynolds Number Quiet Tunnel for Transition Research. AIAA Journal, 13, 300-306.

[6]   Anders, J.B., Stainback, P.C., Keefe, L.R. and Beckwith, I.E. (1977) Fluctuating Disturbances in a Mach-5 Wind Tunnel. AIAA Journal, 15, 1123-1129.

[7]   Beckwith, I.E., Creel, T., Chen, F. and Kendall, J. (1983) Freestream Noise and Transition Measurements on a Cone in a Mach-3.5 Pilot Low-Disturbance Tunnel. NASA-TP-2180.

[8]   Beckwith, I.E., Chen, F.J. and Malik, M.R. (1988) Design and Fabrication Requirements for Low-Noise Supersonic/Hypersonic Wind Tunnels. AIAA Paper: 1988-0143.

[9]   Schneider, S.P. (1998) Design and Fabrication of a 9-Inch Mach-6 Quiet-Flow Ludwieg Tube. AIAA Paper: 1998- 2511.

[10]   Taskinoglu, E.S., Knight, D.D. and Schneider, S.P. (2006) Computational Fluid Dynamics Evaluation of Bleed Slot of the Purdue Mach 6 Quiet Tunnel. AIAA Journal, 44, 1360-1362.

[11]   Aradag, S., Knight, D.D. and Schneider, S.P. (2006) Bleed Lip Geometry Effects on the Flow in a Hypersonic Wind Tunnel. AIAA Journal, 44, 2133-2136.

[12]   Schneider, S.P. (2008) Development of Hypersonic Quiet Tunnels. Journal of Spacecraft and Rockets, 45, 641-664.

[13]   Beckwith, I.E. and Holley, B.B. (1981) G?rtler Vortices and Transition in Wall Boundary Layers of Two Mach-5 Nozzles. NASA-TP-1869.

[14]   Zhou, Y.W., Yi, S.H., Chen, Z., Lu, X.G. and Ge, Y. (2011) The Aerodynamic and Structural Research of Mach 6 Hypersonic Quiet Wind Tunnel. Journal of National University of Defense Technology, 33, 14-17.

[15]   Schneider, S.P., Matsumura, S., Rufer, S., Skoch, C. and Swanson, E. (2002) Progress in the Operation of the Boeing/AFOSR Mach-6 Quiet Tunnel. AIAA Paper: 2002-3033.

[16]   Schneider, S.P., Matsumura, S., Rufer, S., Skock, C. and Swanson, E. (2003) Hypersonic Stability and Transition Experiments on Blunt Cones and a Generic Scramjet Forebody. AIAA Paper: 2003-1130.